Spatially developing supersonic turbulent boundary layer subjected to static surface deformations

The effects of static surface deformations on a spatially developing supersonic boundary layer flow at Mach number M=4 and Reynolds Reδin≈49300, based inflow thickness (δin), are analyzed by performing large eddy simulations. Two low-order structural modes rectangular clamped panel dimensions ≈33δin×48δin prescribed with modal amplitudes δin. these examined the layer, including changes in mean properties, thermal compressibility turbulence structure. results context deviations from concepts typically derived employed for equilibrium turbulence. deflections, to some degree, modify correlations that govern both Morkovin’s hypothesis strong analogy away wall, whereas near-wall region hypotheses breakdown. Modifications structure due elucidated means wall pressure two-point anisotropy invariant maps. In addition amplification turbulence, such lead local separation, instigating low-frequency unsteadiness. One consequence significance practical design is presence low frequency unsteadiness similar encountered impinging or ramp shock interactions.